Error while transforming osculating parameters into mean TLE
Lors de la transformation TLE ->Osc ->TLE du TLE suivant
1 19858U 76077FL 10001.61249236 -.00047525 00000-0 -26271-1 0 9133
2 19858 103.3140 212.2317 0236482 203.2554 155.7430 13.98406682927728
On obtient l'erreur
Exception in thread "main" org.orekit.errors.PropagationException:
réinitialisation de l'état non autorisée
at
org.orekit.propagation.analytical.tle.TLEPropagator.resetInitialState(TLEPropagator.java:471)
at
org.orekit.propagation.conversion.OsculatingToMeanElementsConverter.convert(OsculatingToMeanElementsConverter.java:66)
at MAIN.transformTLE2MeanTLE(MAIN.java:110)
at MAIN.main(MAIN.java:39)
Le code utilisé pour faire cette transformation est:
__final TLEPropagator propagator =
TLEPropagator.selectExtrapolator(tle);
final PVCoordinates pvOsc = propagator.getPVCoordinates(finalDate);
System.out.println("Osculating parameters at epoch " + finalDate);
System.out.println("X " + pvOsc.getPosition().getX());
System.out.println("Y " + pvOsc.getPosition().getY());
System.out.println("Z " + pvOsc.getPosition().getZ());
System.out.println("Vx " + pvOsc.getVelocity().getX());
System.out.println("Vy " + pvOsc.getVelocity().getY());
System.out.println("Vz " + pvOsc.getVelocity().getZ());
// Conversion from osculating elements to mean elements (in TLE sense)
final SpacecraftState oscState = new SpacecraftState(new
CartesianOrbit(pvOsc, frameTEME, finalDate,
CelestialBodyFactory.getEarth().getGM()));
final SpacecraftState meanState = new OsculatingToMeanElementsConverter
(oscState, 1, propagator).convert();**_
_
Ceci semblerait être un bug.
(from redmine: issue id 140, created on 2013-07-05, closed on 2013-07-05)